CN107304716A - A kind of turbine engine failure monitoring method and device - Google Patents
A kind of turbine engine failure monitoring method and device Download PDFInfo
- Publication number
- CN107304716A CN107304716A CN201610255725.4A CN201610255725A CN107304716A CN 107304716 A CN107304716 A CN 107304716A CN 201610255725 A CN201610255725 A CN 201610255725A CN 107304716 A CN107304716 A CN 107304716A
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- China
- Prior art keywords
- compressor inlet
- adjustable vane
- inlet adjustable
- servo control
- actual
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/80—Diagnostics
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The present invention relates to a kind of turbine engine failure monitoring method and device, methods described includes：Obtain compressor inlet adjustable vane aperture set-point and its actual value, compressor inlet adjustable vane SERVO CONTROL given value of current value and its actual value；Compressor inlet adjustable vane aperture set-point and its actual value are compared, compressor inlet adjustable vane SERVO CONTROL given value of current value and its actual value are compared；If compressor inlet adjustable vane SERVO CONTROL current actual value reaches certain time interval T equal to its set-point, and compressor inlet adjustable vane aperture actual value and its set-point are inconsistent, then it is assumed that jam faults occur for compressor inlet adjustable vane, send alarm.Pass through technical scheme, it is possible to achieve monitoring and warning function to compressor inlet adjustable vane jam faults, improve the security of gas turbine operation.The executing agency driven in other hydraulic oil can also be applied simultaneously, and such as fuel speed is than valve and fuel control valve.
Description
Technical field
The present invention relates to gas turbine technology field, in particular to a kind of event of gas turbine
Hinder monitoring method and a kind of turbine engine failure monitoring device.
Background technology
During gas turbine operation, to reach rotating speed of target and target load, it is necessary to operation
Parameter is adjusted, such as into chamber fuel amount and air mass flow.Air mass flow can lead to
The angle of the whole compressor inlet adjustable vane of toning is adjusted, and fuel quantity is compared by fuel speed
Valve and fuel control valve are adjusted.
Thus, the control of operating gas turbine is finally by that can turn to compressor inlet
Stator, the control of liquid fuel and gaseous fuel realizes, and realized by hydraulic oil pair
The control of valve location.
During gas turbine operation, occur that model- following control does not refer to executing agency's action once in a while
The bite of order is obstructed failure, for example than the actual compressor inlet adjustable vane that is referred in invention not
Can follow the failure of given aperture, other executing agencies such as fuel speed of hydraulic oil driving than valve with
Also there is similar failure in fuel control valve.This failure is shut down generally by technical staff and examined
Disconnected analysis is excluded, and is taken time and effort, and influences the economy of gas turbine operation.
The content of the invention
How the technical problems to be solved by the invention, realize that hydraulic oil drive mechanism bite is obstructed
The inline diagnosis function of failure, improves the security and economy of gas turbine operation.
For this purpose, the present invention proposes a kind of Gas turbine fault diagnosis method, including：
S1, obtains given compressor inlet adjustable vane aperture, given compressor inlet is adjustable leads
Leaf SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and actual compressor inlet can
Adjust stator SERVO CONTROL electric current；
S2, by given compressor inlet adjustable vane aperture and actual compressor inlet adjustable vane
Aperture is compared, and gives compressor inlet adjustable vane SERVO CONTROL electric current and actual compressor
Import adjustable vane SERVO CONTROL electric current is compared；
S3, if actual compressor inlet adjustable vane SERVO CONTROL electric current is equal to given compressor and entered
Mouthful adjustable vane SERVO CONTROL electric current reaches certain time interval T, and actual compressor inlet adjustable vane
Aperture and given compressor inlet adjustable vane aperture are inconsistent, then it is assumed that compressor inlet is adjustable
Jam faults occur for stator, send alarm.
Preferably, the given compressor inlet adjustable vane aperture is surveyed according to gas turbine
Rotating speed, gas turbine rotating speed of target, gas turbine actual load and gas turbine target load meter
Obtain；
Wherein gas turbine actual measurement rotating speed is obtained by tachogenerator measurement, and actual load is from generating
Machine is measured, and rotating speed of target is gas turbine rated speed, and target load is given by power network.
Preferably, the given compressor inlet adjustable vane SERVO CONTROL electric current is given calms the anger
Machine import adjustable vane aperture is converted to through signal.
Preferably, the span of the time T is determined by specific executing agency's characteristic.
Preferably, this method is equally applicable to the event of other hydraulic-driven executing agencies of gas turbine
Barrier monitoring, such as natural gas velocity is than valve and natural gas control valve.
The invention also provides a kind of turbine engine failure monitoring device, it is characterised in that including：
Signal acquisition module：Obtain given compressor inlet adjustable vane aperture, given compressor
Import adjustable vane SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and actual pressure
Mechanism of qi import adjustable vane SERVO CONTROL electric current；
Comparison process module：Given compressor inlet adjustable vane aperture and actual compressor are entered
Mouthful adjustable vane aperture is compared, give compressor inlet adjustable vane SERVO CONTROL electric current with
Actual compressor inlet adjustable vane SERVO CONTROL electric current is compared；
Alarm display module：For sending compressor inlet adjustable vane fault alarm.
Preferably, the device can be realized for other hydraulic-driven executing agencies of gas turbine simultaneously
Malfunction monitoring, such as natural gas velocity than valve and natural gas control valve.
Compared with prior art, can be in gas turbine operation process by above-mentioned technical proposal
The middle online self diagnosis for realizing hydraulic oil drive mechanism jam faults, optimizes existing shutdown and examines
Disconnected analysis method, improves the security and economy of gas turbine operation.
Brief description of the drawings
The features and advantages of the present invention can be more clearly understood from by reference to accompanying drawing, accompanying drawing is to show
Meaning property and should not be construed as carrying out the present invention any limitation, in the accompanying drawings：
Fig. 1 shows showing for Gas turbine fault diagnosis method according to an embodiment of the invention
Meaning flow chart；
Fig. 2 shows the knot of Gas turbine fault diagnosis method according to an embodiment of the invention
Structure schematic diagram；
Fig. 3 shows showing for Gas turbine fault diagnosis device according to an embodiment of the invention
Meaning block diagram.
Embodiment
In order to be more clearly understood that the above objects, features and advantages of the present invention, tie below
The drawings and specific embodiments are closed the present invention is further described in detail.Need explanation
It is that, in the case where not conflicting, the feature in embodiments herein and embodiment can be mutual
Combination.
Elaborate many details in the following description to facilitate a thorough understanding of the present invention, but
It is that the present invention can also be different from other modes described here to implement using other, therefore,
Protection scope of the present invention is not limited by following public specific embodiment.
As shown in figure 1, Gas turbine fault diagnosis method according to an embodiment of the invention, bag
Include：
S1, obtains given compressor inlet adjustable vane aperture, given compressor inlet is adjustable leads
Leaf SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and actual compressor inlet can
Adjust stator SERVO CONTROL electric current；
S2, by given compressor inlet adjustable vane aperture and actual compressor inlet adjustable vane
Aperture is compared, and gives compressor inlet adjustable vane SERVO CONTROL electric current and actual compressor
Import adjustable vane SERVO CONTROL electric current is compared；
S3, if actual compressor inlet adjustable vane SERVO CONTROL electric current is equal to given compressor and entered
Mouthful adjustable vane SERVO CONTROL electric current reaches certain time interval T, and actual compressor inlet adjustable vane
Aperture and given compressor inlet adjustable vane aperture are inconsistent, then it is assumed that compressor inlet is adjustable
Jam faults occur for stator, send alarm.
As shown in Fig. 2 the knot of Gas turbine fault diagnosis method according to an embodiment of the invention
Structure, control system 1 is received after the load instruction from power network, can calculate rated speed with bearing
The aperture of compressor inlet adjustable vane under lotus, and the opening degree instruction is sent to compressor inlet
The executing agency 3 of adjustable vane, coordinates the control of fuel quantity, and gas turbine 4 reaches target load,
So as to realize the closed-loop control to gas turbine 4.Fault monitoring device 2 from control system 1 obtain to
Determine compressor inlet adjustable vane aperture, given compressor inlet adjustable vane SERVO CONTROL electric current,
Actual compressor inlet adjustable vane is obtained from the executing agency 3 of compressor inlet adjustable vane to open
Degree and actual compressor inlet adjustable vane SERVO CONTROL electric current.
Preferably, the given compressor inlet adjustable vane aperture is surveyed according to gas turbine
Rotating speed, gas turbine rotating speed of target, gas turbine actual load and gas turbine target load meter
Obtain；
Wherein gas turbine actual measurement rotating speed is obtained by tachogenerator measurement, and actual load is from generating
Machine is measured, and rotating speed of target is gas turbine rated speed, and target load is given by power network.
Preferably, the given compressor inlet adjustable vane SERVO CONTROL electric current is given calms the anger
Machine import adjustable vane aperture is converted to through signal.
Preferably, the span of the time T is determined by specific executing agency's characteristic.
Preferably, this method is equally applicable to the event of other hydraulic-driven executing agencies of gas turbine
Barrier monitoring, such as natural gas velocity is than valve and natural gas control valve.
As shown in figure 3, Gas turbine fault diagnosis device according to an embodiment of the invention, bag
Include：
Signal acquisition module 21：Given compressor inlet adjustable vane aperture is obtained, gives and calms the anger
Machine import adjustable vane SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and reality
Compressor inlet adjustable vane SERVO CONTROL electric current；
Comparison process module 22：By given compressor inlet adjustable vane aperture and actual compressor
Import adjustable vane aperture is compared, and gives compressor inlet adjustable vane SERVO CONTROL electric current
It is compared with actual compressor inlet adjustable vane SERVO CONTROL electric current；
Alarm display module 23：For sending compressor inlet adjustable vane fault alarm.
Preferably, the device can be realized for other hydraulic-driven executing agencies of gas turbine simultaneously
Malfunction monitoring, such as natural gas velocity than valve and natural gas control valve.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention,
For those skilled in the art, the present invention can have various modifications and variations.It is all this
Within the spirit and principle of invention, any modification, equivalent substitution and improvements made etc. all should
Within protection scope of the present invention.
Claims (7)
1. a kind of turbine engine failure monitoring method, it is characterised in that including：
S1, obtains given compressor inlet adjustable vane aperture, given compressor inlet is adjustable leads
Leaf SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and actual compressor inlet can
Adjust stator SERVO CONTROL electric current；
S2, by given compressor inlet adjustable vane aperture and actual compressor inlet adjustable vane
Aperture is compared, and gives compressor inlet adjustable vane SERVO CONTROL electric current and actual compressor
Import adjustable vane SERVO CONTROL electric current is compared；
S3, if actual compressor inlet adjustable vane SERVO CONTROL electric current is equal to given compressor and entered
Mouthful adjustable vane SERVO CONTROL electric current reaches certain time interval T, and actual compressor inlet adjustable vane
Aperture and given compressor inlet adjustable vane aperture are inconsistent, then it is assumed that compressor inlet is adjustable
Jam faults occur for stator, send alarm.
2. turbine engine failure monitoring method according to claim 1, it is characterised in that institute
It is to survey rotating speed, gas turbine according to gas turbine to state given compressor inlet adjustable vane aperture
Rotating speed of target, gas turbine actual load and gas turbine target load calculate what is obtained；
Wherein gas turbine actual measurement rotating speed is obtained by tachogenerator measurement, and actual load is from generating
Machine is measured, and rotating speed of target is gas turbine rated speed, and target load is given by power network.
3. turbine engine failure monitoring method according to claim 1, it is characterised in that institute
It is given compressor inlet adjustable vane to state given compressor inlet adjustable vane SERVO CONTROL electric current
Aperture is converted to through signal.
4. turbine engine failure monitoring method according to claim 1, it is characterised in that institute
The span for stating time T is determined by specific executing agency's characteristic.
5. turbine engine failure monitoring method according to claim 1, it is characterised in that should
Method is equally applicable to the malfunction monitoring of other hydraulic-driven executing agencies of gas turbine, such as natural
Gas velocity is than valve and natural gas control valve.
6. a kind of turbine engine failure monitoring device, it is characterised in that including：
Signal acquisition module：Obtain given compressor inlet adjustable vane aperture, given compressor
Import adjustable vane SERVO CONTROL electric current, actual compressor inlet adjustable vane aperture and actual pressure
Mechanism of qi import adjustable vane SERVO CONTROL electric current；
Comparison process module：Given compressor inlet adjustable vane aperture and actual compressor are entered
Mouthful adjustable vane aperture is compared, give compressor inlet adjustable vane SERVO CONTROL electric current with
Actual compressor inlet adjustable vane SERVO CONTROL electric current is compared；
Alarm display module：For sending compressor inlet adjustable vane fault alarm.
7. turbine engine failure monitoring device according to claim 6, it is characterised in that should
Device can realize the malfunction monitoring for other hydraulic-driven executing agencies of gas turbine simultaneously, such as
Natural gas velocity is than valve and natural gas control valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610255725.4A CN107304716A (en) | 2016-04-22 | 2016-04-22 | A kind of turbine engine failure monitoring method and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610255725.4A CN107304716A (en) | 2016-04-22 | 2016-04-22 | A kind of turbine engine failure monitoring method and device |
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| Publication Number | Publication Date |
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| CN107304716A true CN107304716A (en) | 2017-10-31 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610255725.4A Pending CN107304716A (en) | 2016-04-22 | 2016-04-22 | A kind of turbine engine failure monitoring method and device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107702924A (en) * | 2017-11-21 | 2018-02-16 | 贵州智慧能源科技有限公司 | Monitoring system and its trouble-shooter |
| CN108005795A (en) * | 2017-12-12 | 2018-05-08 | 中国科学院工程热物理研究所 | A kind of compressor inlet guide vane angle real-time control apparatus and method |
| CN109973408A (en) * | 2019-03-26 | 2019-07-05 | 大唐桂冠合山发电有限公司 | The abnormal restoration methods of the movable vane adjustment of adjusting rotor blade section formula pressure fan |
| WO2020152425A1 (en) * | 2019-01-24 | 2020-07-30 | Safran Helicopter Engines | Method for monitoring the operating state of a system for positioning variable-geometry members of a turbomachine |
| CN113294246A (en) * | 2021-06-30 | 2021-08-24 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195730A (en) * | 2013-04-07 | 2013-07-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Compressor inlet rotatable guide vane temperature control method of gas turbine |
-
2016
- 2016-04-22 CN CN201610255725.4A patent/CN107304716A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195730A (en) * | 2013-04-07 | 2013-07-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Compressor inlet rotatable guide vane temperature control method of gas turbine |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107702924A (en) * | 2017-11-21 | 2018-02-16 | 贵州智慧能源科技有限公司 | Monitoring system and its trouble-shooter |
| CN108005795A (en) * | 2017-12-12 | 2018-05-08 | 中国科学院工程热物理研究所 | A kind of compressor inlet guide vane angle real-time control apparatus and method |
| CN108005795B (en) * | 2017-12-12 | 2023-07-21 | 中国科学院工程热物理研究所 | Device and method for controlling angle of inlet guide vane of air compressor in real time |
| WO2020152425A1 (en) * | 2019-01-24 | 2020-07-30 | Safran Helicopter Engines | Method for monitoring the operating state of a system for positioning variable-geometry members of a turbomachine |
| FR3092170A1 (en) * | 2019-01-24 | 2020-07-31 | Safran Helicopter Engines | Method for monitoring the operating state of a positioning system of variable geometry components of a turbomachine |
| CN113330221A (en) * | 2019-01-24 | 2021-08-31 | 赛峰直升机发动机公司 | Method for monitoring the operating state of a system for positioning a variable-geometry component of a turbomachine |
| US11920483B2 (en) | 2019-01-24 | 2024-03-05 | Safran Helicopter Engines | Method for monitoring the operating state of a system for positioning variable-geometry members of a turbomachine |
| CN109973408A (en) * | 2019-03-26 | 2019-07-05 | 大唐桂冠合山发电有限公司 | The abnormal restoration methods of the movable vane adjustment of adjusting rotor blade section formula pressure fan |
| CN113294246A (en) * | 2021-06-30 | 2021-08-24 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
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Application publication date: 20171031 |